US7246774B2 - In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom - Google Patents

In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom Download PDF

Info

Publication number
US7246774B2
US7246774B2 US10/898,601 US89860104A US7246774B2 US 7246774 B2 US7246774 B2 US 7246774B2 US 89860104 A US89860104 A US 89860104A US 7246774 B2 US7246774 B2 US 7246774B2
Authority
US
United States
Prior art keywords
flight refueling
refueling boom
airfoil
boom
rotating
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US10/898,601
Other versions
US20070084968A1 (en
Inventor
German von Thal
Harry W. Slusher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Assigned to BOEING COMPANY, THE reassignment BOEING COMPANY, THE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SLUSHER, HARRY W., THAL, GERMAN VON
Priority to US10/898,601 priority Critical patent/US7246774B2/en
Priority to DE602005012838T priority patent/DE602005012838D1/en
Priority to ES05856876T priority patent/ES2321431T3/en
Priority to EP05856876A priority patent/EP1784332B1/en
Priority to AT05856876T priority patent/ATE423062T1/en
Priority to PCT/US2005/024605 priority patent/WO2006085986A1/en
Publication of US20070084968A1 publication Critical patent/US20070084968A1/en
Publication of US7246774B2 publication Critical patent/US7246774B2/en
Application granted granted Critical
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D39/00—Refuelling during flight

Definitions

  • the present invention relates generally to in-flight refueling of a manned or unmanned aircraft using a boom in-flight refueling system, and specifically, providing a rotating device configured to surround an in-flight refueling boom, wherein the rotating device is operably engaged with an airfoil, such that the in-flight refueling boom may be pivoted through a horizontal and vertical range of motion due to the cooperation of the rotating device with the airfoil operably engaged therewith.
  • In-flight refueling is an important method for extending the range of both manned and unmanned aircraft traveling long distances over areas having no feasible landing or refueling points.
  • in-flight refueling is a relatively common operation, especially for military aircraft, precise positioning of a second aircraft (the receiver aircraft, for example) with respect to a first aircraft (the tanker aircraft, for example) is required in order to provide a safe engagement of the first aircraft (and a refueling system carried thereby) with the second aircraft for the dispensing of fuel.
  • the requirement of precise relative spatial positioning of two rapidly moving aircraft makes in-flight refueling a challenging operation.
  • the boom in-flight refueling system typically comprises a rigid boom carried by and lowered from a rear portion of a fuselage of a first aircraft.
  • the aft end of the boom includes an extendable tube with a refueling nozzle attached to its aft end.
  • the forward end of the boom is attached to the first aircraft and may be pivoted in the vertical and lateral directions.
  • Near the aft end of the boom are airfoils, which may be controlled by an in-flight refueling system operator onboard the first aircraft.
  • the airfoils provide maneuverability of the boom with respect to an aircraft that is to be refueled (the second aircraft) and allow the in-flight refueling operator to position the boom relative to the second aircraft, by for instance, actuating the airfoils so as to “fly” the boom to a refueling position relative to the second aircraft.
  • an operator of the second aircraft must maneuver the second aircraft to within an in-flight refueling position, below and aft of the first aircraft.
  • the in-flight refueling system operator may control the airfoils to position the boom such that the extendable refueling nozzle of the boom may be extended to engage a refueling receptacle on the second aircraft.
  • the in-flight refueling system operator is responsible for maintaining the position of the boom relative to the refueling receptacle as the refueling nozzle is extended towards the second aircraft.
  • the in-flight refueling system operator may have limited control of the in-flight refueling boom, due to the range of motion of the in-flight refueling boom and the airfoils attached thereto, as described below.
  • the airfoils are attached to an end of the boom and radially extend from the boom in a “V” configuration such that the airfoils may be configured to control the in-flight refueling boom through both a vertical range of motion (elevation, for instance) and a horizontal range of motion (azimuth, for instance).
  • the airfoils typically rotate only about a torque tube defined by within the airfoil (wherein the torque tube may be positioned anywhere within the airfoil or along a leading edge of the airfoil, the leading edge being an edge of the airfoil nearest the tanker aircraft).
  • the airfoils of conventional boom in-flight refueling systems may have a relatively limited range of motion such that they may be ineffective in controlling the in-flight refueling boom outside of a limited elevation and azimuth range.
  • the in-flight refueling operator may not be able to adequately control to the in-flight refueling boom to engage a refueling receptacle carried by a second aircraft when the second aircraft approaches the tanker aircraft from a position outside the relatively limited range of motion of the in-flight refueling boom.
  • This may be problematic in cases wherein, for instance, the second aircraft is a large aircraft, such as for instance a bomber aircraft or airlift aircraft having a large amount of control inertia.
  • the second aircraft may be forced to abort the approach to the tanker aircraft and return for another approach in an attempt to attain a position relative to the tanker aircraft wherein the limited range of motion of the in-flight refueling boom will allow it to become engaged with the refueling receptacle carried by the second aircraft.
  • the delay incurred by having to retry a tanker approach in this manner may be detrimental to military missions having critical time constraints.
  • the second aircraft may have very little fuel remaining upon approaching the tanker aircraft, such that it may be critical to the safety of the second aircraft and the crew aboard that the first tanker approach results in a refueling engagement with the in-flight refueling boom.
  • the in-flight refueling operator may have improved control over the in-flight refueling boom so as to more effectively engage a refueling receptacle carried by the second aircraft even in cases where the second aircraft approaches the tanker aircraft from a position outside the most optimal in-flight refueling position.
  • an in-flight refueling system, boom, and method that provides for an increased range of elevation and azimuth travel for the in-flight refueling boom, relative to the tanker aircraft from which it extends during an in-flight refueling operation.
  • an airfoil operably engaged with an in-flight refueling boom such that the airfoil has an expanded range of motion so as to have the capability of guiding the in-flight refueling boom through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems.
  • the in-flight refueling system and in-flight refueling boom of the present invention provide an airfoil operably engaged with an in-flight refueling boom extending from a tanker aircraft, wherein the airfoil is configured to be capable of rotating about the in-flight refueling boom so as to position the in-flight refueling boom relative to the tanker aircraft by guiding the in-flight refueling boom through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems.
  • the in-flight refueling system of the present invention includes a tanker aircraft comprising a fuselage; an in-flight refueling boom defining a longitudinal axis and configured to be carried by the tanker aircraft so as to extend from the fuselage of the tanker aircraft; and at least one airfoil operably engaged with, and extending radially outward from the in-flight refueling boom.
  • the at least one airfoil is further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom so as to position the in-flight refueling boom relative to the fuselage of the tanker aircraft.
  • the in-flight refueling system and in-flight refueling boom of the present invention may further include a rotating device, operably engaged with the in-flight refueling boom and configured to substantially surround a portion of the in-flight refueling boom.
  • the rotating device may be operably engaged with the at least one airfoil and may be configured to cooperate with the end of the in-flight refueling boom and the at least one airfoil such that the at least one airfoil may be capable of rotating about the longitudinal axis of the in-flight refueling boom.
  • the rotating device may be further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom.
  • the at least one airfoil may be further configured to be capable of rotating with respect to the rotating device about the longitudinal axis of the in-flight refueling boom.
  • the in-flight refueling system and in-flight refueling boom of one embodiment may further comprise a controller operably engaged with the in-flight refueling boom wherein the controller is configured to rotate the at least one airfoil about the in-flight refueling boom.
  • the embodiments of the present invention also provide a method for positioning an in-flight refueling boom relative to a tanker aircraft configured to carry the in-flight refueling boom.
  • the method of one embodiment rotates at least one airfoil that is operably engaged with, and that extends radially outward from, the in-flight refueling boom about the longitudinal axis of the in-flight refueling boom so as to position the in-flight refueling boom relative to the fuselage of the tanker aircraft.
  • the rotation may include rotating a rotating device that is configured to substantially surround a portion of the in-flight refueling boom and that operably engages the at least one airfoil about the longitudinal axis of the in-flight refueling boom.
  • the at least one airfoil may rotate with the rotating device about the longitudinal axis of the in-flight refueling boom.
  • the various embodiments of the in-flight refueling system, in-flight refueling boom, and method of the present invention provide many advantages that may include, but are not limited to: providing an in-flight refueling system wherein the in-flight refueling boom has greater maneuverability that an in-flight refueling boom of a conventional boom in-flight refueling system, and providing an in-flight refueling boom capable of a greater range of motion through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems.
  • advantages of the present invention include, the ability to rotate at least one airfoil about a longitudinal axis of the in-flight refueling boom so as to allow the at least one airfoil to be stowed in a position relative to a tanker aircraft that may be aerodynamically advantageous to the tanker aircraft while in flight.
  • FIG. 1 shows a tanker aircraft and an in-flight refueling boom extending therefrom;
  • FIG. 2 shows an in-flight refueling boom and a pair of airfoils operably engaged therewith according to one embodiment of the in-flight refueling system of the present invention
  • FIG. 3 shows a rear view of an in-flight refueling boom and a pair of airfoils operably engaged therewith wherein the airfoils are rotated so as to be disposed about 180 degrees apart;
  • FIG. 4 shows a rear view of an in-flight refueling boom having a rotating device and a pair of airfoils operably engaged therewith according to one embodiment of the present invention
  • FIG. 5 shows a rear view of an in-flight refueling boom of the present invention as well as a range of elevation and azimuth travel though which the in-flight refueling boom may travel relative to a neutral trailing position aft and below a tanker aircraft.
  • FIG. 1 of the present invention shows a boom in-flight refueling system according to one embodiment of the present invention wherein an in-flight refueling boom 114 is carried by, and extended from, a tanker aircraft 110 such that the tanker aircraft 110 may be configured to conduct an in-flight refueling operation by using, for instance, an airfoil 118 (such as, for instance, a ruddervator), to maneuver the in-flight refueling boom 114 such that an extendable nozzle 116 may be extended therefrom so as to engage a refueling receptacle carried by a second aircraft (not shown) that may be positioned to the rear and aft of the tanker aircraft 110 .
  • an airfoil 118 such as, for instance, a ruddervator
  • the airfoil 118 may be configured to be actuated by an operator of the in-flight refueling system so as to cause the in-flight refueling boom 114 to be pivoted about a pivoting device 115 (such as, for instance, a pintle) so as to maneuver the in-flight refueling boom 114 into a refueling position relative to the second aircraft.
  • a pivoting device 115 such as, for instance, a pintle
  • the in-flight refueling system may comprise a tanker aircraft 110 , an in-flight refueling boom 114 defining a longitudinal axis 120 , wherein the in-flight refueling boom 114 is configured to be carried by and extend from the tanker aircraft 110 , and at least one airfoil 118 a , 118 b extending radially outward from the in-flight refueling boom 114 .
  • the in-flight refueling system may comprise a first airfoil 118 a and a second airfoil 118 b configured to be capable of rotating about the longitudinal axis 120 of the in-flight refueling boom 114 so as to pivot the in-flight refueling boom 114 relative to the fuselage of the tanker aircraft 110 . While an in-flight refueling system having two airfoils 118 a , 118 b is described, the in-flight refueling system could have any number of airfoils.
  • the airfoils 118 a , 118 b include a torque tube 220 (or other hinging device) extending outward from a support fitting 215 that may be attached to the in-flight refueling boom 114 .
  • the torque tube 220 could be located within the airfoil 118 a , 118 b at any location that is aerodynamically and structurally advantageous.
  • the torque tube 220 may be disposed in a central portion of the airfoil 118 a , 118 b or, in some instances, along a leading edge of the airfoil 118 a , 118 b that may be disposed substantially upstream in an air flow from a corresponding trailing edge 225 .
  • the airfoil 118 a , 118 b may thus rotate in the support fitting 215 , about the centerline of the torque tube 220 (or other hinging device) such that the airfoil 118 a , 118 b may act as a control surface (similar to an aileron and/or rudder) so as to impart lift, drag, and/or other control inputs to the in-flight refueling boom 114 so as to further maneuver the in-flight refueling boom 114 relative to the pivot device 115 .
  • a control surface similar to an aileron and/or rudder
  • an operator of the in-flight refueling system may control the airfoils 118 a , 118 b , and thus, the in-flight refueling boom 114 so that the in-flight refueling boom 114 may engage a refueling receptacle carried by a second aircraft (not shown) that may approach a refueling position aft and below the tanker aircraft 110 .
  • the support fitting 215 of the airfoils 118 a , 118 b may be configured to extend into and be operably engaged with a channel 210 defined in the in-flight refueling boom 114 ( FIG. 3 ) or a collar mounted thereon ( FIG. 4 ) such that the airfoils 118 a , 118 b may be configured to rotate through the channel 210 and about the longitudinal axis 120 of the in-flight refueling boom 114 .
  • the trailing edges 225 a , 225 b of the two airfoils 118 a , 118 b may be capable of rotating about a respective support fitting 215 a , 215 b so as to provide control inputs to the in-flight refueling boom 114 as it is trailed behind the tanker aircraft 110 during an in-flight refueling operation.
  • the in-flight refueling boom 114 may be pivoted through an enlarged elevation 320 and azimuth 330 with respect to the pivot device 115 . As shown in FIG.
  • the embodiments of the present invention may allow the airfoils 118 a , 118 b to rotate about the in-flight refueling boom 114 such that the range of elevation 320 and azimuth 330 travel of the in-flight refueling boom 114 may be expanded when compared to conventional in-flight refueling systems having a pair of airfoils arranged in a fixed “V” configuration with respect to the in-flight refueling boom.
  • the airfoils 118 a , 118 b may be rotated about the in-flight refueling boom 114 within the channels 210 a , 210 b defined in the in-flight refueling boom 114 such that the airfoils may be positioned about the longitudinal axis 120 of the in-flight refueling boom 114 and separated by, for instance, a separation angle 310 .
  • the in-flight refueling boom 114 generally defines one circumferentially extending channel 210 for each airfoil 118 .
  • Each channel extends through a pre-defined angular range, such as an angular range of about 150 degrees, that defines the maximum angular range through which the airfoil 118 may be moved.
  • a pre-defined angular range such as an angular range of about 150 degrees
  • the airfoils 118 a , 118 b may be positioned about 180 degrees apart at about the 3 o'clock and 9 o'clock positions relative to the longitudinal axis 120 of the in-flight refueling boom 114 .
  • the airfoils 118 a , 118 b , and the trailing edges 225 a , 225 b thereof, may impart a greater vertical force on the in-flight refueling boom 114 so as to increase the elevation 320 through which the in-flight refueling boom 114 may travel with respect to the pivot device 115 .
  • the airfoils 118 a , 118 b may be advantageously positioned with a separation angle of about 180 degrees as the in-flight refueling boom 114 is pivoted upwards and stowed with respect to a rear portion of the fuselage of the tanker aircraft 110 .
  • the airfoils 118 a , 118 b may be positioned so as to impart additional lift and/or stability to the rear of the tanker aircraft 110 as the in-flight refueling boom 114 is stowed with respect to the tanker aircraft 110 .
  • the airfoils 118 a 118 b may alternatively be positioned such that the separation angle 310 between the airfoils 118 a , 118 b may be substantially less, such as about 60 degrees, such that the first airfoil 118 a may be positioned at about the 11 o'clock position and the second airfoil 118 b may be positioned at about the 1 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114 .
  • the airfoils 118 a , 118 b , and the trailing edges 225 a , 225 b thereof may impart a greater horizontal force on the in-flight refueling boom 114 as the so as to increase the azimuth 330 (or horizontal range of motion) through which the in-flight refueling boom 114 may travel with respect to the pivot device 115 .
  • the airfoils 118 a , 118 b of the present invention may be rotated about the in-flight refueling boom 114 in the channels 210 a , 210 b defined therein so as to assume a suitable separation angle 310 so as to impart a vertical and/or horizontal control input to the in-flight refueling boom 114 .
  • each of the first airfoil 118 a and the second airfoil 118 b may be actuated independently such that, for instance, the first airfoil 118 a may be rotated to a substantially horizontal position (such as about the 9 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114 ) and the second airfoil 118 b may be rotated to a substantially vertical position (such as about the 12 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114 ).
  • This relative position of the airfoils 118 a , 118 b may allow the in-flight refueling boom 114 to be movable partially through a range of elevation 320 (by actuating the trailing edge 225 a of the first airfoil 118 a (acting substantially as an aileron) and to be movable partially through a range of azimuth 330 (by actuating the trailing edge 225 b of the first airfoil (acting substantially as a rudder)).
  • an operator of the in-flight refueling system may control each airfoil 118 a , 118 b independently or in unison to as to provide suitable control inputs to the in-flight refueling boom 114 so as to enable the safe and expeditious engagement thereof with a refueling receptacle carried by a second aircraft.
  • FIG. 4 shows another embodiment of the in-flight refueling system, boom, and assembly of the present invention further comprising a rotating device 410 , such as, for instance, a collar device, operably engaged with and configured to substantially surround a portion of the in-flight refueling boom 114 (typically a portion of the distal end of the in-flight refueling boom 114 ).
  • the rotating device 410 may substantially surround and be configured to rotate about, the in-flight refueling boom 114 .
  • the rotating device 410 may be seated in an indentation circumferentially defined in the surface of the in-flight refueling boom 114 .
  • the indentation may comprise a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof in order to secure and actuate the rotating device 410 within the indentation and to cause the rotating device 410 to rotate about the in-flight refueling boom 114 .
  • the indentation may provide a smooth conductive and/or magnetic surface suitable for interacting with the rotating device 410 wherein the rotating device 410 may comprise a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof suitable for rotating the rotating device 410 about the in-flight refueling boom 114 (or the indentation defined therein).
  • the rotating device 410 may comprise a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof suitable for rotating the rotating device 410 about the in-flight refueling boom 114 (or the indentation defined therein).
  • the rotating device 410 may be in communication with a controller 113 (as described more fully below) configured to rotate the rotating device 114 about the in-flight refueling boom 114 via, for instance, a electrical, hydraulic, or electromechanical connection between the rotating device 410 and the in-flight refueling boom 114 .
  • the rotating device 410 may operably engage the airfoils 118 a , 118 b and may be further configured to cooperate with the in-flight refueling boom 114 and the airfoils 118 a , 118 b such that the airfoils 118 a , 118 b may rotate about the in-flight refueling boom 114 . As shown in FIG.
  • the rotating device 410 may further define a pair of channels 210 a , 210 b that may be configured to receive the support fittings 215 a , 215 b attached to the torque tubes 220 a , 220 b of the airfoils 118 a , 118 b .
  • the airfoils 118 a , 118 b may be rotated relative to and through the respective channels 210 a , 210 b defined by the rotating device 410 (and/or the in-flight refueling boom 114 ) and relative to one another so as to be separated by any desired separation angle 310 within a pre-defined range as described above.
  • the in-flight refueling boom 114 of this embodiment need not define additional channels.
  • the airfoils 118 a , 118 b may also be affixed to or otherwise adapted to rotate with the rotating device 410 such that the separation angle 410 remains fixed between the airfoils 118 a , 118 b .
  • the rotating device 410 may be configured to be capable of rotating about the in-flight refueling boom such that the airfoils 118 a , 118 b (fixed with respect to each other and separated by a selectively fixed separation angle 310 ) may be rotated concurrently about the in-flight refueling boom 114 .
  • the airfoils 118 a , 118 b may be capable of rotating individually with respect to channels 210 a , 210 b defined in a rotating device 410 that may further rotate about the in-flight refueling boom 114 .
  • This configuration may allow for more precise control of the control surfaces (such as the trailing edges 225 a , 225 b ) of the airfoils 118 a , 118 b such that the airfoils 118 a , 118 b may more precisely pivot the in-flight refueling boom 114 through a range of elevation 320 and azimuth 330 (see FIG.
  • the airfoils 118 a , 118 b may be first rotated relative to and through the respective channels 210 a , 210 b defined by the rotating device 410 so as to be separated by any desired separation angle 310 . Then, the airfoils 118 a , 118 b may also be affixed to or otherwise adapted to rotate with the rotating device 410 such that the separation angle 410 remains fixed between the airfoils 118 a , 118 b .
  • an optimum separation angle 310 may be achieved between the airfoils 118 a , 118 b so as to achieve an enlarged range of elevation 320 and/or azimuth 330 travel for the in-flight refueling boom 114 relative to the pivot device 115 , and the airfoils may then be rotated about the in-flight refueling boom 114 (while either maintaining or adjusting the separation angle 310 ) so as to precisely guide the in-flight refueling boom 114 through the range of elevation 320 and azimuth 330 .
  • the airfoils 118 a , 118 b may each be fixed with respect to one of a pair of rotating devices 410 configured to substantially surround and to be capable of rotating about the in-flight refueling boom 114 (in, for instance, an indentation defined therein).
  • an aft rotating device may be configured to be operably engaged with the first airfoil 118 a and a forward rotating device may be configured to be operably engaged with the second airfoil 118 b .
  • each airfoil 118 a , 118 b may be rotated relative to the other so as to achieve a selected separation angle 310 and subsequently the airfoils 118 a , 118 b may be rotated in unison (by rotating each of the forward and aft rotating devices 410 in unison).
  • the independent rotation of each rotating device 410 about the in-flight refueling boom 114 (and the resulting independent rotation of the airfoils 118 a , 118 b extending therefrom) may preclude the need for channels 210 a , 210 b to be defined in either the in-flight refueling boom 114 or the rotating device 410 .
  • the channel 210 may comprise an actuating mechanism 111 , such as a radial actuating track configured to carry the support fitting 215 and the airfoil 118 extending therefrom.
  • a pair of channels 210 a , 210 b may also comprise complementary actuating mechanisms 111 (such as, for instance, bearing tracks) configured to retain the support fittings 215 a , 215 b such that the airfoils 118 a , 118 b extending therefrom may be actuated with respect to the in-flight refueling boom 114 along the channels 210 a , 210 b defined in the in-flight refueling boom 114 .
  • the support fittings 215 a , 215 b are engaged by the channel (or an actuating mechanism 111 disposed in conjunction therewith) so as to secure the airfoils 118 a , 118 b to the in-flight refueling boom 114 and/or the rotating device 410 .
  • the airfoils 118 a , 118 b may be actuated by the actuating mechanism 111 so as to move within the channels 210 a , 210 b by hydraulic, electrical, mechanical, or other mechanisms such that the airfoils 118 a , 118 b may be configured to be capable of rotating with respect to the longitudinal axis 120 of the in-flight refueling boom 114 .
  • a linear induction motor disposed substantially within the channels 210 a , 210 b may provide the motive force so as to move the airfoils either individually, or in tandem, in response to control signals received from a controller 113 (discussed below).
  • the support fittings 215 a , 215 b may be held in place within the channels 210 via a bearing assembly that may be constrained such that the support fittings 215 a , 215 b may be movable by, for instance, a linear induction motor, through the radial angular range defined by the channels 210 , but may be constrained against being pulled radially outward from the channel 210 .
  • the airfoils 118 a , 118 b may be composed, for instance, of lightweight materials (such as, for instance, carbon fiber composite materials) so as to decrease the weight load experienced by the support fittings 215 a , 215 b and/or the complementary bearing assembly disposed within the channel 210 that may be utilized to secure the support fittings 215 a , 215 b .
  • lightweight materials such as, for instance, carbon fiber composite materials
  • the rotating device 410 may also comprise an actuating mechanism 111 such as a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof suitable for rotating the rotating device 410 about the in-flight refueling boom 114 .
  • the rotating device 410 may be in communication with a controller 113 (as described more fully below) configured to rotate the rotating device 410 (and the airfoils 118 a , 118 b extending therefrom), about the in-flight refueling boom 114 via, for instance, an electromechanical connection between the rotating device 410 and the in-flight refueling boom 114 .
  • the rotating device 410 may, in some embodiments, be configured to be seated in an indentation defined in the in-flight refueling boom 114 wherein the indentation may further comprise a magnetic and/or conductive surface suitable for interacting with the rotating device 410 and causing the rotation thereof with respect to the in-flight refueling boom 114 .
  • the airfoils 118 a , 118 b and/or the rotating device 410 may be in communication with a controller 113 configured to send control inputs to the actuating mechanism 111 disposed within the channels 210 a , 210 b such as a linear induction motor or the like, to cause the actuating mechanism 111 to rotate the airfoils 118 a , 118 b about the longitudinal axis 120 of the in-flight refueling boom 114 , as described above.
  • a controller 113 configured to send control inputs to the actuating mechanism 111 disposed within the channels 210 a , 210 b such as a linear induction motor or the like, to cause the actuating mechanism 111 to rotate the airfoils 118 a , 118 b about the longitudinal axis 120 of the in-flight refueling boom 114 , as described above.
  • the controller 113 may further comprise one or more microprocessors (or other computer devices) and/or input and output devices such that an operator of the in-flight refueling system may monitor and/or control the operation of the controller 113 if required.
  • the controller 113 may be in communication with the actuating mechanism 111 (disposed, for instance, within the channels 210 a , 210 b ) and, in turn, the airfoils 118 a , 118 b and/or the rotating device 410 so as to control the separation angle 310 between the airfoils 118 a , 118 b (in embodiments in which the separation angle 310 can vary) and the radial position of each airfoil 118 a , 118 b with respect to the longitudinal axis 120 .
  • the controller 113 may provide control signals to the actuating mechanism 111 to cause the airfoils 118 a , 118 b to rotate about their respective support fittings 215 a , 215 b so as to position the trailing edges 225 a , 225 b of the respective airfoils 118 a , 118 b relative to the torque tubes 220 a , 220 b (which may, as described below be positioned along the leading edges of the airfoils 118 a , 118 b or within a center portion of the airfoils 118 a , 118 b ).
  • the pivoting of the in-flight refueling boom 114 through a range of elevation 320 and azimuth 330 is more effectively controlled with respect to the pivot device 115 operably engaged with the tanker aircraft 110 .
  • controller 113 may be in communication with the actuating mechanism 111 via various devices and methods suitable for controlling the actuating mechanism 111 , including hydraulic lines, electromechanical devices and/or methods, as well as via electronic connections in communication with one or more electromechanical servo motors operably engaged with the airfoils 118 a , 118 b (which may be known by those skilled in the art as a “fly-by-wire” control system).
  • the controller 113 may also be in communication with the rotating device 410 via an actuating mechanism 111 (which may be included within the rotating device) such that the controller 113 may substantially control the rotating device 410 and cause the rotating device 410 (and the airfoils 118 a , 118 b , operably engaged therewith) to be rotated about the in-flight refueling boom.
  • an actuating mechanism 111 which may be included within the rotating device
  • the controller 113 may substantially control the rotating device 410 and cause the rotating device 410 (and the airfoils 118 a , 118 b , operably engaged therewith) to be rotated about the in-flight refueling boom.
  • a rotating device 410 that also defines channels 210 a , 210 b therein (see generally, FIG.
  • the controller 410 may be configured to be capable of controlling both the actuation of the airfoils 118 a , 118 b within the channels 210 a , 210 b as well as the general rotation of the rotating device 410 about the in-flight refueling boom 114 .
  • the controller 113 may be configured to be capable of adjusting both the separation angle 310 between adjacent airfoils 118 a , 118 b by controlling the movement of the airfoils 118 a , 118 b within their respective channels 210 a , 210 b as well as the radial position of the rotating device 410 about the in-flight refueling boom 114 which controls or sets the angle through which the airfoils 118 a , 118 b may be moved.
  • the controller 113 may be disposed within a fuselage of the tanker aircraft 110 .
  • the controller 113 may be positioned near an operator of the in-flight refueling system such as, for instance, in a remote aerial refueling operator (RARO) station disposed near a forward end of the fuselage of the tanker aircraft 110 .
  • RARO remote aerial refueling operator
  • the controller 113 may further comprise, control inputs and/or output devices such that the operator of the in-flight refueling system may view images of the in-flight refueling operation and provide control inputs to the controller 113 so as to actuate the airfoils 118 a , 118 b operably engaged with the end of the in-flight refueling boom 114 . As described in more detail above, and shown generally in FIG.
  • the controller 113 may direct the actuating mechanism 111 (disposed for instance, within the channels 210 a , 210 b ) to rotate the airfoils 118 a , 118 b about the in-flight refueling boom 114 so as to adjust both the angular position of each of the airfoils 118 a , 118 b as well as the separation angle 310 between the airfoils 118 a , 118 b .
  • the actuating mechanism 111 disposed for instance, within the channels 210 a , 210 b
  • the controller 113 may direct the actuating mechanism 111 (disposed for instance, within the channels 210 a , 210 b ) to rotate the airfoils 118 a , 118 b about the in-flight refueling boom 114 so as to adjust both the angular position of each of the airfoils 118 a , 118 b as well as the separation angle 310 between the airfoils 118
  • the airfoils 118 a , 118 b may be positioned relative to the in-flight refueling boom 114 so as to more effectively pivot the in-flight refueling boom 114 relative to the pivot device 115 such that the in-flight refueling boom 114 may be pivoted through a range of elevation 320 and azimuth 330 relative to the pivot device 115 .
  • the controller 113 may translate, for instance, control inputs from the operator of the in-flight refueling system into a series of commands to the actuating mechanism 111 such that the in-flight refueling boom 114 may be pivoted and positioned relative to the tanker aircraft 110 so as to be more capable of completing an in-flight refueling operation with a second aircraft (not shown).
  • FIG. 5 shows a schematic representation of the range of elevation 320 and azimuth 330 positions that may be attainable by an end of the in-flight refueling boom 114 having the benefit of the advantages provided by some embodiments of the present invention.
  • the ability to rotate one or more of the airfoils 118 a , 118 b relative to the in-flight refueling boom 114 may further allow the in-flight refueling boom 114 to be pivoted through an extended range of elevation 320 and azimuth 330 relative to the pivot device 115 carried by the tanker aircraft 110 .
  • the various embodiments of the present invention may allow, for instance, the in-flight refueling boom 114 to be positioned so as to be capable of engaging (by extending, for instance, the extendable nozzle 116 ) a refueling receptacle carried by a second aircraft (not shown) that may approach the tanker aircraft 110 from outside the range of motion 510 of a conventional boom in-flight refueling system.
  • the controller 113 of the present invention may provide precise control over the airfoils 118 a , 118 b so as to more safely and effectively engage a refueling receptacle carried by a second aircraft.
  • a method according to one embodiment of the present invention is provided for positioning an in-flight refueling boom 114 defining a longitudinal axis 120 , relative to a tanker aircraft 110 (see FIG. 1 ) configured to carry the in-flight refueling boom 114 such that the in-flight refueling boom 114 is configured to extend below and aft of a fuselage of the tanker aircraft 114 and to pivot about a pivot device 115 carried by the tanker aircraft 110 .
  • the method comprises rotating at least one airfoil 118 operably engaged with, and extending radially outward from, the in-flight refueling boom 114 , about the longitudinal axis 120 of the in-flight refueling boom 114 so as to pivot the in-flight refueling boom 114 relative to the fuselage of the tanker aircraft 110 .
  • this rotation may further comprise (as shown in FIG. 4 ) rotating a rotating device 410 that is configured to substantially surround a portion of the in-flight refueling boom 114 about the longitudinal axis 120 of the in-flight refueling boom 114 .
  • the rotating device 410 may operably engage (and/or control) the at least one airfoil 118 a , 118 b (as described more particularly above).
  • the rotation of the rotating device 410 may also rotate the at least one airfoil 118 a , 118 b that is operably engaged therewith.
  • the at least one airfoil 118 a , 118 b may be rotated about the in-flight refueling boom 114 .

Abstract

An in-flight refueling system, boom, and method are provided for extending the range of motion of an in-flight refueling boom carried by a first aircraft so as to facilitate an in-flight refueling operation between the first and the second aircraft. More specifically, in some embodiments the present invention provides a rotating device, operably engaged with at least one airfoil, and configured to substantially surround and rotate about the in-flight refueling boom such that the rotating device and the at least one airfoil operably engaged therewith, may be actuated so as to extend the range of motion of the in-flight refueling boom.

Description

FIELD OF THE INVENTION
The present invention relates generally to in-flight refueling of a manned or unmanned aircraft using a boom in-flight refueling system, and specifically, providing a rotating device configured to surround an in-flight refueling boom, wherein the rotating device is operably engaged with an airfoil, such that the in-flight refueling boom may be pivoted through a horizontal and vertical range of motion due to the cooperation of the rotating device with the airfoil operably engaged therewith.
BACKGROUND OF THE INVENTION
In-flight refueling (or air-to-air refueling) is an important method for extending the range of both manned and unmanned aircraft traveling long distances over areas having no feasible landing or refueling points. Although in-flight refueling is a relatively common operation, especially for military aircraft, precise positioning of a second aircraft (the receiver aircraft, for example) with respect to a first aircraft (the tanker aircraft, for example) is required in order to provide a safe engagement of the first aircraft (and a refueling system carried thereby) with the second aircraft for the dispensing of fuel. The requirement of precise relative spatial positioning of two rapidly moving aircraft makes in-flight refueling a challenging operation.
One conventional system for in-flight refueling is the boom in-flight refueling system. The boom in-flight refueling system typically comprises a rigid boom carried by and lowered from a rear portion of a fuselage of a first aircraft. The aft end of the boom includes an extendable tube with a refueling nozzle attached to its aft end. The forward end of the boom is attached to the first aircraft and may be pivoted in the vertical and lateral directions. Near the aft end of the boom are airfoils, which may be controlled by an in-flight refueling system operator onboard the first aircraft. The airfoils provide maneuverability of the boom with respect to an aircraft that is to be refueled (the second aircraft) and allow the in-flight refueling operator to position the boom relative to the second aircraft, by for instance, actuating the airfoils so as to “fly” the boom to a refueling position relative to the second aircraft. First, an operator of the second aircraft must maneuver the second aircraft to within an in-flight refueling position, below and aft of the first aircraft. Upon maneuvering into the in-flight refueling position, the in-flight refueling system operator on board the tanker aircraft may control the airfoils to position the boom such that the extendable refueling nozzle of the boom may be extended to engage a refueling receptacle on the second aircraft. The in-flight refueling system operator is responsible for maintaining the position of the boom relative to the refueling receptacle as the refueling nozzle is extended towards the second aircraft. The in-flight refueling system operator, however, may have limited control of the in-flight refueling boom, due to the range of motion of the in-flight refueling boom and the airfoils attached thereto, as described below.
In conventional boom in-flight refueling systems, the airfoils are attached to an end of the boom and radially extend from the boom in a “V” configuration such that the airfoils may be configured to control the in-flight refueling boom through both a vertical range of motion (elevation, for instance) and a horizontal range of motion (azimuth, for instance). According to conventional systems, the airfoils typically rotate only about a torque tube defined by within the airfoil (wherein the torque tube may be positioned anywhere within the airfoil or along a leading edge of the airfoil, the leading edge being an edge of the airfoil nearest the tanker aircraft). As such, the airfoils of conventional boom in-flight refueling systems may have a relatively limited range of motion such that they may be ineffective in controlling the in-flight refueling boom outside of a limited elevation and azimuth range. As such, the in-flight refueling operator may not be able to adequately control to the in-flight refueling boom to engage a refueling receptacle carried by a second aircraft when the second aircraft approaches the tanker aircraft from a position outside the relatively limited range of motion of the in-flight refueling boom. This may be problematic in cases wherein, for instance, the second aircraft is a large aircraft, such as for instance a bomber aircraft or airlift aircraft having a large amount of control inertia. In such cases, it may be difficult for an operator of the second aircraft to adjust the position of the second aircraft relative to the first aircraft and the second aircraft may be forced to abort the approach to the tanker aircraft and return for another approach in an attempt to attain a position relative to the tanker aircraft wherein the limited range of motion of the in-flight refueling boom will allow it to become engaged with the refueling receptacle carried by the second aircraft. The delay incurred by having to retry a tanker approach in this manner may be detrimental to military missions having critical time constraints. In addition, the second aircraft may have very little fuel remaining upon approaching the tanker aircraft, such that it may be critical to the safety of the second aircraft and the crew aboard that the first tanker approach results in a refueling engagement with the in-flight refueling boom.
Thus, it would be advantageous to improve the range of motion of the airfoils such that the range of elevation and azimuth travel of the in-flight refueling boom (relative to the tanker aircraft) may be expanded relative to conventional boom in-flight refueling systems. This may, in turn, allow the in-flight refueling operator to have improved control over the in-flight refueling boom so as to more effectively engage a refueling receptacle carried by the second aircraft even in cases where the second aircraft approaches the tanker aircraft from a position outside the most optimal in-flight refueling position.
Therefore, there exists a need for an in-flight refueling system, boom, and method that provides for an increased range of elevation and azimuth travel for the in-flight refueling boom, relative to the tanker aircraft from which it extends during an in-flight refueling operation. Thus, there exists a need for an airfoil operably engaged with an in-flight refueling boom such that the airfoil has an expanded range of motion so as to have the capability of guiding the in-flight refueling boom through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems.
SUMMARY OF THE INVENTION
The embodiments of the present invention satisfy the needs listed above and provide other advantages as described below. The in-flight refueling system and in-flight refueling boom of the present invention provide an airfoil operably engaged with an in-flight refueling boom extending from a tanker aircraft, wherein the airfoil is configured to be capable of rotating about the in-flight refueling boom so as to position the in-flight refueling boom relative to the tanker aircraft by guiding the in-flight refueling boom through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems. The in-flight refueling system of the present invention includes a tanker aircraft comprising a fuselage; an in-flight refueling boom defining a longitudinal axis and configured to be carried by the tanker aircraft so as to extend from the fuselage of the tanker aircraft; and at least one airfoil operably engaged with, and extending radially outward from the in-flight refueling boom. The at least one airfoil is further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom so as to position the in-flight refueling boom relative to the fuselage of the tanker aircraft.
According to other embodiments, the in-flight refueling system and in-flight refueling boom of the present invention may further include a rotating device, operably engaged with the in-flight refueling boom and configured to substantially surround a portion of the in-flight refueling boom. Furthermore, the rotating device may be operably engaged with the at least one airfoil and may be configured to cooperate with the end of the in-flight refueling boom and the at least one airfoil such that the at least one airfoil may be capable of rotating about the longitudinal axis of the in-flight refueling boom. According to some embodiments the rotating device may be further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom. The at least one airfoil may be further configured to be capable of rotating with respect to the rotating device about the longitudinal axis of the in-flight refueling boom. The in-flight refueling system and in-flight refueling boom of one embodiment may further comprise a controller operably engaged with the in-flight refueling boom wherein the controller is configured to rotate the at least one airfoil about the in-flight refueling boom.
The embodiments of the present invention also provide a method for positioning an in-flight refueling boom relative to a tanker aircraft configured to carry the in-flight refueling boom. The method of one embodiment rotates at least one airfoil that is operably engaged with, and that extends radially outward from, the in-flight refueling boom about the longitudinal axis of the in-flight refueling boom so as to position the in-flight refueling boom relative to the fuselage of the tanker aircraft. In this regard, the rotation may include rotating a rotating device that is configured to substantially surround a portion of the in-flight refueling boom and that operably engages the at least one airfoil about the longitudinal axis of the in-flight refueling boom. As such, the at least one airfoil may rotate with the rotating device about the longitudinal axis of the in-flight refueling boom.
Thus the various embodiments of the in-flight refueling system, in-flight refueling boom, and method of the present invention provide many advantages that may include, but are not limited to: providing an in-flight refueling system wherein the in-flight refueling boom has greater maneuverability that an in-flight refueling boom of a conventional boom in-flight refueling system, and providing an in-flight refueling boom capable of a greater range of motion through an expanded range of elevation and azimuth travel relative to conventional boom in-flight refueling systems. Other advantages of the present invention include, the ability to rotate at least one airfoil about a longitudinal axis of the in-flight refueling boom so as to allow the at least one airfoil to be stowed in a position relative to a tanker aircraft that may be aerodynamically advantageous to the tanker aircraft while in flight.
These advantages and others that will be evident to those skilled in the art are provided in the in-flight refueling system, in-flight refueling boom, and method of the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
Having thus described the invention in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and wherein:
FIG. 1 shows a tanker aircraft and an in-flight refueling boom extending therefrom;
FIG. 2 shows an in-flight refueling boom and a pair of airfoils operably engaged therewith according to one embodiment of the in-flight refueling system of the present invention;
FIG. 3 shows a rear view of an in-flight refueling boom and a pair of airfoils operably engaged therewith wherein the airfoils are rotated so as to be disposed about 180 degrees apart;
FIG. 4 shows a rear view of an in-flight refueling boom having a rotating device and a pair of airfoils operably engaged therewith according to one embodiment of the present invention; and
FIG. 5 shows a rear view of an in-flight refueling boom of the present invention as well as a range of elevation and azimuth travel though which the in-flight refueling boom may travel relative to a neutral trailing position aft and below a tanker aircraft.
 DETAILED DESCRIPTION OF THE INVENTION
The present inventions now will be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the invention are shown. Indeed, these inventions may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will satisfy applicable legal requirements. Like numbers refer to like elements throughout.
FIG. 1 of the present invention shows a boom in-flight refueling system according to one embodiment of the present invention wherein an in-flight refueling boom 114 is carried by, and extended from, a tanker aircraft 110 such that the tanker aircraft 110 may be configured to conduct an in-flight refueling operation by using, for instance, an airfoil 118 (such as, for instance, a ruddervator), to maneuver the in-flight refueling boom 114 such that an extendable nozzle 116 may be extended therefrom so as to engage a refueling receptacle carried by a second aircraft (not shown) that may be positioned to the rear and aft of the tanker aircraft 110. The airfoil 118 may be configured to be actuated by an operator of the in-flight refueling system so as to cause the in-flight refueling boom 114 to be pivoted about a pivoting device 115 (such as, for instance, a pintle) so as to maneuver the in-flight refueling boom 114 into a refueling position relative to the second aircraft.
More particularly, as shown in FIGS. 1 and 2, the in-flight refueling system according to one embodiment of the present invention may comprise a tanker aircraft 110, an in-flight refueling boom 114 defining a longitudinal axis 120, wherein the in-flight refueling boom 114 is configured to be carried by and extend from the tanker aircraft 110, and at least one airfoil 118 a, 118 b extending radially outward from the in-flight refueling boom 114. As shown in FIGS. 2 and 3, the in-flight refueling system may comprise a first airfoil 118 a and a second airfoil 118 b configured to be capable of rotating about the longitudinal axis 120 of the in-flight refueling boom 114 so as to pivot the in-flight refueling boom 114 relative to the fuselage of the tanker aircraft 110. While an in-flight refueling system having two airfoils 118 a, 118 b is described, the in-flight refueling system could have any number of airfoils. The airfoils 118 a, 118 b include a torque tube 220 (or other hinging device) extending outward from a support fitting 215 that may be attached to the in-flight refueling boom 114. The torque tube 220 could be located within the airfoil 118 a, 118 b at any location that is aerodynamically and structurally advantageous. For instance, in some embodiments the torque tube 220 may be disposed in a central portion of the airfoil 118 a, 118 b or, in some instances, along a leading edge of the airfoil 118 a, 118 b that may be disposed substantially upstream in an air flow from a corresponding trailing edge 225. The airfoil 118 a, 118 b may thus rotate in the support fitting 215, about the centerline of the torque tube 220 (or other hinging device) such that the airfoil 118 a, 118 b may act as a control surface (similar to an aileron and/or rudder) so as to impart lift, drag, and/or other control inputs to the in-flight refueling boom 114 so as to further maneuver the in-flight refueling boom 114 relative to the pivot device 115. As such, an operator of the in-flight refueling system may control the airfoils 118 a, 118 b, and thus, the in-flight refueling boom 114 so that the in-flight refueling boom 114 may engage a refueling receptacle carried by a second aircraft (not shown) that may approach a refueling position aft and below the tanker aircraft 110.
Furthermore, according to embodiments of the present invention, the support fitting 215 of the airfoils 118 a, 118 b may be configured to extend into and be operably engaged with a channel 210 defined in the in-flight refueling boom 114 (FIG. 3) or a collar mounted thereon (FIG. 4) such that the airfoils 118 a, 118 b may be configured to rotate through the channel 210 and about the longitudinal axis 120 of the in-flight refueling boom 114. In addition to rotating the airfoils 118 a, 118 b about the longitudinal axis 120, the trailing edges 225 a, 225 b of the two airfoils 118 a, 118 b may be capable of rotating about a respective support fitting 215 a, 215 b so as to provide control inputs to the in-flight refueling boom 114 as it is trailed behind the tanker aircraft 110 during an in-flight refueling operation. By controllably rotating the airfoils 118 a, 118 b about the longitudinal axis 120 of the in-flight refueling boom 114 and correspondingly actuating their respective trailing edges 225 a, 225 b, the in-flight refueling boom 114 may be pivoted through an enlarged elevation 320 and azimuth 330 with respect to the pivot device 115. As shown in FIG. 5 and described more particularly below, the embodiments of the present invention may allow the airfoils 118 a, 118 b to rotate about the in-flight refueling boom 114 such that the range of elevation 320 and azimuth 330 travel of the in-flight refueling boom 114 may be expanded when compared to conventional in-flight refueling systems having a pair of airfoils arranged in a fixed “V” configuration with respect to the in-flight refueling boom.
As shown in FIG. 3, the airfoils 118 a, 118 b may be rotated about the in-flight refueling boom 114 within the channels 210 a, 210 b defined in the in-flight refueling boom 114 such that the airfoils may be positioned about the longitudinal axis 120 of the in-flight refueling boom 114 and separated by, for instance, a separation angle 310. The in-flight refueling boom 114 generally defines one circumferentially extending channel 210 for each airfoil 118. Each channel extends through a pre-defined angular range, such as an angular range of about 150 degrees, that defines the maximum angular range through which the airfoil 118 may be moved. For example, as shown in FIG. 3, the airfoils 118 a, 118 b may be positioned about 180 degrees apart at about the 3 o'clock and 9 o'clock positions relative to the longitudinal axis 120 of the in-flight refueling boom 114. As such, the airfoils 118 a, 118 b, and the trailing edges 225 a, 225 b thereof, may impart a greater vertical force on the in-flight refueling boom 114 so as to increase the elevation 320 through which the in-flight refueling boom 114 may travel with respect to the pivot device 115. In addition, one skilled in the art will appreciate that as the airfoils 118 a, 118 b may be advantageously positioned with a separation angle of about 180 degrees as the in-flight refueling boom 114 is pivoted upwards and stowed with respect to a rear portion of the fuselage of the tanker aircraft 110. In such a position, the airfoils 118 a, 118 b may be positioned so as to impart additional lift and/or stability to the rear of the tanker aircraft 110 as the in-flight refueling boom 114 is stowed with respect to the tanker aircraft 110.
According to the various embodiments of the present invention, the airfoils 118 a 118 b may alternatively be positioned such that the separation angle 310 between the airfoils 118 a, 118 b may be substantially less, such as about 60 degrees, such that the first airfoil 118 a may be positioned at about the 11 o'clock position and the second airfoil 118 b may be positioned at about the 1 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114. In such a position, the airfoils 118 a, 118 b, and the trailing edges 225 a, 225 b thereof, may impart a greater horizontal force on the in-flight refueling boom 114 as the so as to increase the azimuth 330 (or horizontal range of motion) through which the in-flight refueling boom 114 may travel with respect to the pivot device 115. In addition, depending on the control inputs required to maneuver the in-flight refueling boom 114 into an in-flight refueling position relative to a refueling receptacle carried by a second aircraft, the airfoils 118 a, 118 b of the present invention may be rotated about the in-flight refueling boom 114 in the channels 210 a, 210 b defined therein so as to assume a suitable separation angle 310 so as to impart a vertical and/or horizontal control input to the in-flight refueling boom 114. In addition, each of the first airfoil 118 a and the second airfoil 118 b may be actuated independently such that, for instance, the first airfoil 118 a may be rotated to a substantially horizontal position (such as about the 9 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114) and the second airfoil 118 b may be rotated to a substantially vertical position (such as about the 12 o'clock position relative to the longitudinal axis 120 of the in-flight refueling boom 114). This relative position of the airfoils 118 a, 118 b may allow the in-flight refueling boom 114 to be movable partially through a range of elevation 320 (by actuating the trailing edge 225 a of the first airfoil 118 a (acting substantially as an aileron) and to be movable partially through a range of azimuth 330 (by actuating the trailing edge 225 b of the first airfoil (acting substantially as a rudder)). In addition, an operator of the in-flight refueling system (or the controller 113 operably engaged with the airfoils 118 a, 118 b and/or channels 210 a, 210 b, as described more fully below) may control each airfoil 118 a, 118 b independently or in unison to as to provide suitable control inputs to the in-flight refueling boom 114 so as to enable the safe and expeditious engagement thereof with a refueling receptacle carried by a second aircraft.
FIG. 4 shows another embodiment of the in-flight refueling system, boom, and assembly of the present invention further comprising a rotating device 410, such as, for instance, a collar device, operably engaged with and configured to substantially surround a portion of the in-flight refueling boom 114 (typically a portion of the distal end of the in-flight refueling boom 114). The rotating device 410 may substantially surround and be configured to rotate about, the in-flight refueling boom 114. In some instances, the rotating device 410 may be seated in an indentation circumferentially defined in the surface of the in-flight refueling boom 114. Furthermore, the indentation may comprise a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof in order to secure and actuate the rotating device 410 within the indentation and to cause the rotating device 410 to rotate about the in-flight refueling boom 114. In other embodiments, the indentation may provide a smooth conductive and/or magnetic surface suitable for interacting with the rotating device 410 wherein the rotating device 410 may comprise a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof suitable for rotating the rotating device 410 about the in-flight refueling boom 114 (or the indentation defined therein). According to some advantageous embodiments, the rotating device 410 may be in communication with a controller 113 (as described more fully below) configured to rotate the rotating device 114 about the in-flight refueling boom 114 via, for instance, a electrical, hydraulic, or electromechanical connection between the rotating device 410 and the in-flight refueling boom 114. The rotating device 410 may operably engage the airfoils 118 a, 118 b and may be further configured to cooperate with the in-flight refueling boom 114 and the airfoils 118 a, 118 b such that the airfoils 118 a, 118 b may rotate about the in-flight refueling boom 114. As shown in FIG. 4, the rotating device 410 may further define a pair of channels 210 a, 210 b that may be configured to receive the support fittings 215 a, 215 b attached to the torque tubes 220 a, 220 b of the airfoils 118 a, 118 b. Thus, according to some embodiments, the airfoils 118 a, 118 b may be rotated relative to and through the respective channels 210 a, 210 b defined by the rotating device 410 (and/or the in-flight refueling boom 114) and relative to one another so as to be separated by any desired separation angle 310 within a pre-defined range as described above. As a result of the channels 210 a, 210 b defined by the rotating device 410, the in-flight refueling boom 114 of this embodiment need not define additional channels.
Instead of permitting rotation of the airfoils 118 a, 118 b relative to the rotating device 410 so as to controllably vary the separation angle 310 therebetween, the airfoils 118 a, 118 b may also be affixed to or otherwise adapted to rotate with the rotating device 410 such that the separation angle 410 remains fixed between the airfoils 118 a, 118 b. In this embodiment, the rotating device 410 may be configured to be capable of rotating about the in-flight refueling boom such that the airfoils 118 a, 118 b (fixed with respect to each other and separated by a selectively fixed separation angle 310) may be rotated concurrently about the in-flight refueling boom 114. In some embodiments, as shown in FIG. 4, the airfoils 118 a, 118 b may be capable of rotating individually with respect to channels 210 a, 210 b defined in a rotating device 410 that may further rotate about the in-flight refueling boom 114. This configuration may allow for more precise control of the control surfaces (such as the trailing edges 225 a, 225 b) of the airfoils 118 a, 118 b such that the airfoils 118 a, 118 b may more precisely pivot the in-flight refueling boom 114 through a range of elevation 320 and azimuth 330 (see FIG. 3) with respect to the pivot device 115 that may be carried by the tanker aircraft 110. For instance, the airfoils 118 a, 118 b may be first rotated relative to and through the respective channels 210 a, 210 b defined by the rotating device 410 so as to be separated by any desired separation angle 310. Then, the airfoils 118 a, 118 b may also be affixed to or otherwise adapted to rotate with the rotating device 410 such that the separation angle 410 remains fixed between the airfoils 118 a, 118 b. Thus, an optimum separation angle 310 may be achieved between the airfoils 118 a, 118 b so as to achieve an enlarged range of elevation 320 and/or azimuth 330 travel for the in-flight refueling boom 114 relative to the pivot device 115, and the airfoils may then be rotated about the in-flight refueling boom 114 (while either maintaining or adjusting the separation angle 310) so as to precisely guide the in-flight refueling boom 114 through the range of elevation 320 and azimuth 330.
Furthermore, in some embodiments, the airfoils 118 a, 118 b may each be fixed with respect to one of a pair of rotating devices 410 configured to substantially surround and to be capable of rotating about the in-flight refueling boom 114 (in, for instance, an indentation defined therein). In such an embodiment, an aft rotating device may be configured to be operably engaged with the first airfoil 118 a and a forward rotating device may be configured to be operably engaged with the second airfoil 118 b. Thus, each airfoil 118 a, 118 b may be rotated relative to the other so as to achieve a selected separation angle 310 and subsequently the airfoils 118 a, 118 b may be rotated in unison (by rotating each of the forward and aft rotating devices 410 in unison). In such embodiments, the independent rotation of each rotating device 410 about the in-flight refueling boom 114 (and the resulting independent rotation of the airfoils 118 a, 118 b extending therefrom) may preclude the need for channels 210 a, 210 b to be defined in either the in-flight refueling boom 114 or the rotating device 410.
According to some embodiments as shown in FIG. 2, the channel 210 may comprise an actuating mechanism 111, such as a radial actuating track configured to carry the support fitting 215 and the airfoil 118 extending therefrom. Furthermore, as shown in FIG. 3, a pair of channels 210 a, 210 b may also comprise complementary actuating mechanisms 111 (such as, for instance, bearing tracks) configured to retain the support fittings 215 a, 215 b such that the airfoils 118 a, 118 b extending therefrom may be actuated with respect to the in-flight refueling boom 114 along the channels 210 a, 210 b defined in the in-flight refueling boom 114. In either instance, the support fittings 215 a, 215 b are engaged by the channel (or an actuating mechanism 111 disposed in conjunction therewith) so as to secure the airfoils 118 a, 118 b to the in-flight refueling boom 114 and/or the rotating device 410. The airfoils 118 a, 118 b may be actuated by the actuating mechanism 111 so as to move within the channels 210 a, 210 b by hydraulic, electrical, mechanical, or other mechanisms such that the airfoils 118 a, 118 b may be configured to be capable of rotating with respect to the longitudinal axis 120 of the in-flight refueling boom 114. For example, a linear induction motor disposed substantially within the channels 210 a, 210 b may provide the motive force so as to move the airfoils either individually, or in tandem, in response to control signals received from a controller 113 (discussed below). In addition, the support fittings 215 a, 215 b may be held in place within the channels 210 via a bearing assembly that may be constrained such that the support fittings 215 a, 215 b may be movable by, for instance, a linear induction motor, through the radial angular range defined by the channels 210, but may be constrained against being pulled radially outward from the channel 210. In some embodiments, the airfoils 118 a, 118 b may be composed, for instance, of lightweight materials (such as, for instance, carbon fiber composite materials) so as to decrease the weight load experienced by the support fittings 215 a, 215 b and/or the complementary bearing assembly disposed within the channel 210 that may be utilized to secure the support fittings 215 a, 215 b. Moreover, in conjunction with the embodiment of FIG. 4, the rotating device 410 may also comprise an actuating mechanism 111 such as a radial electric motor; a radial induction motor; a radial electromechanical device; a circular ball bearing assembly; an actuator track; and combinations thereof suitable for rotating the rotating device 410 about the in-flight refueling boom 114. According to some advantageous embodiments, the rotating device 410 may be in communication with a controller 113 (as described more fully below) configured to rotate the rotating device 410 (and the airfoils 118 a, 118 b extending therefrom), about the in-flight refueling boom 114 via, for instance, an electromechanical connection between the rotating device 410 and the in-flight refueling boom 114. As described above, the rotating device 410 may, in some embodiments, be configured to be seated in an indentation defined in the in-flight refueling boom 114 wherein the indentation may further comprise a magnetic and/or conductive surface suitable for interacting with the rotating device 410 and causing the rotation thereof with respect to the in-flight refueling boom 114.
Furthermore, and as shown generally in FIGS. 1 and 3, the airfoils 118 a, 118 b and/or the rotating device 410 may be in communication with a controller 113 configured to send control inputs to the actuating mechanism 111 disposed within the channels 210 a, 210 b such as a linear induction motor or the like, to cause the actuating mechanism 111 to rotate the airfoils 118 a, 118 b about the longitudinal axis 120 of the in-flight refueling boom 114, as described above. The controller 113 may further comprise one or more microprocessors (or other computer devices) and/or input and output devices such that an operator of the in-flight refueling system may monitor and/or control the operation of the controller 113 if required. The controller 113 may be in communication with the actuating mechanism 111 (disposed, for instance, within the channels 210 a, 210 b) and, in turn, the airfoils 118 a, 118 b and/or the rotating device 410 so as to control the separation angle 310 between the airfoils 118 a, 118 b (in embodiments in which the separation angle 310 can vary) and the radial position of each airfoil 118 a, 118 b with respect to the longitudinal axis 120. Additionally, the controller 113 may provide control signals to the actuating mechanism 111 to cause the airfoils 118 a, 118 b to rotate about their respective support fittings 215 a, 215 b so as to position the trailing edges 225 a, 225 b of the respective airfoils 118 a, 118 b relative to the torque tubes 220 a, 220 b (which may, as described below be positioned along the leading edges of the airfoils 118 a, 118 b or within a center portion of the airfoils 118 a, 118 b). By adjusting the position of the trailing edges 225 a, 225 b of the airfoils 118 a, 118 b in conjunction with the radial positioning steps described above, the pivoting of the in-flight refueling boom 114 through a range of elevation 320 and azimuth 330 is more effectively controlled with respect to the pivot device 115 operably engaged with the tanker aircraft 110. Furthermore, the controller 113 may be in communication with the actuating mechanism 111 via various devices and methods suitable for controlling the actuating mechanism 111, including hydraulic lines, electromechanical devices and/or methods, as well as via electronic connections in communication with one or more electromechanical servo motors operably engaged with the airfoils 118 a, 118 b (which may be known by those skilled in the art as a “fly-by-wire” control system).
As noted above, in some embodiments, such as that shown generally in FIG. 4, the controller 113 may also be in communication with the rotating device 410 via an actuating mechanism 111 (which may be included within the rotating device) such that the controller 113 may substantially control the rotating device 410 and cause the rotating device 410 (and the airfoils 118 a, 118 b, operably engaged therewith) to be rotated about the in-flight refueling boom. Also, in embodiments of the present invention comprising a rotating device 410 that also defines channels 210 a, 210 b therein (see generally, FIG. 4), the controller 410 may be configured to be capable of controlling both the actuation of the airfoils 118 a, 118 b within the channels 210 a, 210 b as well as the general rotation of the rotating device 410 about the in-flight refueling boom 114. Thus, the controller 113 may be configured to be capable of adjusting both the separation angle 310 between adjacent airfoils 118 a, 118 b by controlling the movement of the airfoils 118 a, 118 b within their respective channels 210 a, 210 b as well as the radial position of the rotating device 410 about the in-flight refueling boom 114 which controls or sets the angle through which the airfoils 118 a, 118 b may be moved.
As shown generally in FIG. 1, the controller 113 may be disposed within a fuselage of the tanker aircraft 110. In some embodiments, the controller 113 may be positioned near an operator of the in-flight refueling system such as, for instance, in a remote aerial refueling operator (RARO) station disposed near a forward end of the fuselage of the tanker aircraft 110. The controller 113 may further comprise, control inputs and/or output devices such that the operator of the in-flight refueling system may view images of the in-flight refueling operation and provide control inputs to the controller 113 so as to actuate the airfoils 118 a, 118 b operably engaged with the end of the in-flight refueling boom 114. As described in more detail above, and shown generally in FIG. 4, the controller 113 may direct the actuating mechanism 111 (disposed for instance, within the channels 210 a, 210 b) to rotate the airfoils 118 a, 118 b about the in-flight refueling boom 114 so as to adjust both the angular position of each of the airfoils 118 a, 118 b as well as the separation angle 310 between the airfoils 118 a, 118 b. As such, the airfoils 118 a, 118 b may be positioned relative to the in-flight refueling boom 114 so as to more effectively pivot the in-flight refueling boom 114 relative to the pivot device 115 such that the in-flight refueling boom 114 may be pivoted through a range of elevation 320 and azimuth 330 relative to the pivot device 115. Thus, the controller 113 may translate, for instance, control inputs from the operator of the in-flight refueling system into a series of commands to the actuating mechanism 111 such that the in-flight refueling boom 114 may be pivoted and positioned relative to the tanker aircraft 110 so as to be more capable of completing an in-flight refueling operation with a second aircraft (not shown).
FIG. 5 shows a schematic representation of the range of elevation 320 and azimuth 330 positions that may be attainable by an end of the in-flight refueling boom 114 having the benefit of the advantages provided by some embodiments of the present invention. Also shown in schematic is a range of motion 510 for an in-flight refueling boom fitted with a fixed (i.e., non-rotatable with respect to the longitudinal axis 120 of the in-flight refueling boom 114) pair of airfoils configured in an upright “V” configuration as in a conventional boom in-flight refueling system. As shown, the ability to rotate one or more of the airfoils 118 a, 118 b relative to the in-flight refueling boom 114 may further allow the in-flight refueling boom 114 to be pivoted through an extended range of elevation 320 and azimuth 330 relative to the pivot device 115 carried by the tanker aircraft 110. Thus, the various embodiments of the present invention may allow, for instance, the in-flight refueling boom 114 to be positioned so as to be capable of engaging (by extending, for instance, the extendable nozzle 116) a refueling receptacle carried by a second aircraft (not shown) that may approach the tanker aircraft 110 from outside the range of motion 510 of a conventional boom in-flight refueling system. In addition, the controller 113 of the present invention may provide precise control over the airfoils 118 a, 118 b so as to more safely and effectively engage a refueling receptacle carried by a second aircraft.
Referring again to FIG. 2, a method according to one embodiment of the present invention is provided for positioning an in-flight refueling boom 114 defining a longitudinal axis 120, relative to a tanker aircraft 110 (see FIG. 1) configured to carry the in-flight refueling boom 114 such that the in-flight refueling boom 114 is configured to extend below and aft of a fuselage of the tanker aircraft 114 and to pivot about a pivot device 115 carried by the tanker aircraft 110. In one embodiment, the method comprises rotating at least one airfoil 118 operably engaged with, and extending radially outward from, the in-flight refueling boom 114, about the longitudinal axis 120 of the in-flight refueling boom 114 so as to pivot the in-flight refueling boom 114 relative to the fuselage of the tanker aircraft 110.
According to other embodiments, this rotation may further comprise (as shown in FIG. 4) rotating a rotating device 410 that is configured to substantially surround a portion of the in-flight refueling boom 114 about the longitudinal axis 120 of the in-flight refueling boom 114. The rotating device 410 may operably engage (and/or control) the at least one airfoil 118 a, 118 b (as described more particularly above). As noted above, the rotation of the rotating device 410 may also rotate the at least one airfoil 118 a, 118 b that is operably engaged therewith. In this regard, the at least one airfoil 118 a, 118 b may be rotated about the in-flight refueling boom 114.
Many modifications and other embodiments of the invention will come to mind to one skilled in the art to which this invention pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Therefore, it is to be understood that the invention is not to be limited to the specific embodiments disclosed and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.

Claims (20)

1. An in-flight refueling system comprising:
a tanker aircraft comprising a fuselage;
an in-flight refueling boom defining a longitudinal axis, the in-flight refueling boom configured to be carried by the tanker aircraft and to extend from the fuselage thereof;
and at least one airfoil operably engaged with, and extending radially outward from, the longitudinal axis of the in-flight refueling boom, the at least one airfoil being configured to be capable of rotating separately about the in-flight refueling boom so as to pivot the in-flight refueling boom relative to the fuselage of the tanker aircraft.
2. An in-flight refueling system according to claim 1, further comprising a rotating device, operably engaged with and configured to substantially surround a portion of the in-flight refueling boom, the rotating device being operably engaged with the at least one airfoil and configured to cooperate with the end of the in-flight refueling boom and the at least one airfoil such that the at least one airfoil is configured to be capable of rotating about the in-flight refueling boom.
3. An in-flight refueling system according to claim 2, wherein the rotating device is further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom.
4. An in-flight refueling system according to claim 2, wherein the at least one airfoil is further configured to be capable of rotating with the rotating device about the longitudinal axis of the in-flight refueling boom.
5. An in-flight refueling system according to claim 1, further comprising a controller configured to rotate the at least one airfoil about the longitudinal axis of the in-flight refueling boom.
6. An in-flight refueling system according to claim 2, wherein the rotating device is selected from the group consisting of:
a radial electric motor;
a radial induction motor;
a radial electromechanical device;
a circular ball bearing assembly;
an actuator track; and
combinations thereof.
7. An in-flight refueling boom defining a longitudinal axis and being adapted to extend from a fuselage of a tanker aircraft, the in-flight refueling boom comprising: at least one airfoil operably engaged with, and extending radially outward from, the longitudinal axis of the in-flight refueling boom, the at least one airfoil being configured to be capable of rotating separately about the in-flight refueling boom so as to pivot the in-flight refueling boom relative to the fuselage of the tanker aircraft.
8. An in-flight refueling boom according to claim 7, further comprising a rotating device, operably engaged with and configured to substantially surround a portion of the in-flight refueling boom, the rotating device being operably engaged with the at least one airfoil and configured to cooperate with the end of the in-flight refueling boom and the at least one airfoil such that the at least one airfoil is configured to be capable of rotating about the in-flight refueling boom.
9. An in-flight refueling boom according to claim 8, wherein the rotating device is further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom.
10. An in-flight refueling boom according to claim 8, wherein the at least one airfoil is further configured to be capable of rotating with the rotating device about the longitudinal axis of the in-flight refueling boom.
11. An in-flight refueling boom according to claim 7, further comprising a controller configured to rotate the at least one airfoil about the longitudinal axis of the in-flight refueling boom.
12. An in-flight refueling boom according to claim 8, wherein the rotating device is selected from the group consisting of:
a radial electric motor;
a radial induction motor;
a radial electromechanical device;
a circular ball bearing assembly;
an actuator track; and
combinations thereof.
13. An assembly adapted to operably engage a refueling boom defining a longitudinal axis, the in-flight refueling boom being adapted to be carried by a tanker aircraft and to extend from a fuselage thereof, the assembly comprising:
at least one airfoil operably engaged with, and extending radially outward from, the longitudinal axis of the in-flight refueling boom, the at least one airfoil being configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom so as to pivot the in-flight refueling boom relative to the fuselage of the tanker aircraft; and
a rotating device, operably engaged with and configured to substantially surround a portion of the in-flight refueling boom, the rotating device being operably engaged with the at least one airfoil and configured to cooperate with the end of the in-flight refueling boom and the at least one airfoil such that the at least one airfoil is configured to be capable of rotating separately about the in-flight refueling boom so as to extend a range of motion of the in-flight refueling boom relative to the fuselage of the tanker aircraft.
14. An assembly according to claim 13, wherein the rotating device is further configured to be capable of rotating about the longitudinal axis of the in-flight refueling boom.
15. An assembly according to claim 13, wherein the at least one airfoil is further configured to be capable of rotating with the rotating device about the longitudinal axis of the in-flight refueling boom.
16. An assembly according to claim 13, further comprising a controller configured to rotate the at least one airfoil about the longitudinal axis of the in-flight refueling boom.
17. An assembly according to claim 13, wherein the rotating device is selected from the group consisting of:
a radial electric motor;
a radial induction motor;
a radial electromechanical device;
a circular ball bearing assembly;
an actuator track; and
combinations thereof.
18. A method for positioning an in-flight refueling boom defining a longitudinal axis, relative to a tanker aircraft configured to carry the in-flight refueling boom, the method comprising:
rotating at least one airfoil separately about the in-flight refueling boom so as to pivot the in-flight refueling boom relative to the fuselage of the tanker aircraft, the at least one airfoil operably engaged with, and extending radially outward from, the longitudinal axis of the in-flight refueling boom.
19. A method according to claim 18, wherein the rotating step further comprises rotating a rotating device that is configured to substantially surround a portion of the in-flight refueling boom and that operably engages the at least one airfoil, wherein rotating the rotating device comprises rotating the rotating device about the in-flight refueling boom.
20. A method according to claim 18, wherein the rotating step further comprises rotating the at least one airfoil with a rotating device that is configured to substantially surround a portion of the in-flight refueling boom and is operably engaged with the at least one airfoil, wherein rotating the at least one airfoil comprises rotating the at least one airfoil about the in-flight refueling boom.
US10/898,601 2004-07-23 2004-07-23 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom Expired - Fee Related US7246774B2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US10/898,601 US7246774B2 (en) 2004-07-23 2004-07-23 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom
AT05856876T ATE423062T1 (en) 2004-07-23 2005-07-11 IN-FLIGHT REFUELING SYSTEM, BOOM AND METHOD FOR EXTENDING A SERIES OF IN-FLIGHT REFUELING MOVEMENTS
ES05856876T ES2321431T3 (en) 2004-07-23 2005-07-11 FLIGHT REAPROVISIONING SYSTEM, EXTENSIBLE ARM AND MOVEMENT LEVEL EXTENSION PROCEDURE IN AN EXTENSIBLE FLIGHT REAPROVISIONING ARM.
EP05856876A EP1784332B1 (en) 2004-07-23 2005-07-11 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom
DE602005012838T DE602005012838D1 (en) 2004-07-23 2005-07-11 SYSTEM FOR FILLING DURING THE FLIGHT, BOOM AND METHOD FOR EXTENDING A SERIES OF MOVEMENTS TO FILLING DURING THE FLIGHT
PCT/US2005/024605 WO2006085986A1 (en) 2004-07-23 2005-07-11 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/898,601 US7246774B2 (en) 2004-07-23 2004-07-23 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom

Publications (2)

Publication Number Publication Date
US20070084968A1 US20070084968A1 (en) 2007-04-19
US7246774B2 true US7246774B2 (en) 2007-07-24

Family

ID=36609546

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/898,601 Expired - Fee Related US7246774B2 (en) 2004-07-23 2004-07-23 In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom

Country Status (6)

Country Link
US (1) US7246774B2 (en)
EP (1) EP1784332B1 (en)
AT (1) ATE423062T1 (en)
DE (1) DE602005012838D1 (en)
ES (1) ES2321431T3 (en)
WO (1) WO2006085986A1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8439311B2 (en) 2010-08-23 2013-05-14 The Boeing Company Aerial refueling boom and boom pivot
US20140042274A1 (en) * 2012-08-09 2014-02-13 The Boeing Company Refueling Boom Control System
US9150311B2 (en) 2012-01-04 2015-10-06 Israel Aerospace Industries Ltd. Systems and methods for air vehicles
US20160075441A1 (en) * 2014-09-12 2016-03-17 Ziad Ahmed Mohamed Ali Hussein Elsawah Aerial refueling navigable device, system and method
US10011181B2 (en) 2016-09-27 2018-07-03 Ford Global Technologies, Llc Vehicle-to-vehicle charging system
US10132628B2 (en) 2015-03-06 2018-11-20 The Boeing Company Aerial refueling boom elevation estimation system
US11465768B2 (en) 2017-07-10 2022-10-11 Israel Aerospace Industries Ltd. Refueling device
US11919655B2 (en) 2017-06-18 2024-03-05 Israel Aerospace Industries Ltd. System and method for refueling air vehicles

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7959110B2 (en) * 2007-04-11 2011-06-14 The Boeing Company Methods and apparatus for resisting torsional loads in aerial refueling booms
EP2168869B1 (en) * 2007-06-15 2014-10-29 EADS Construcciones Aeronauticas, S.A. Device for reducing the cross-stream force generated by the section of air refuelling booms
US7850121B2 (en) * 2007-10-12 2010-12-14 The Boeing Company Enhanced ruddevator for improved air refueling boom flight control
GB2454512A (en) 2007-11-09 2009-05-13 Flight Refueling Ltd Steerable drogue for in-flight refuelling
EP2738097B1 (en) 2012-11-29 2015-10-07 Airbus Defence and Space SA In-Flight refueling systems with a digital communication sub-system
US11691753B2 (en) * 2019-11-11 2023-07-04 Textron Innovations Inc. Systems and methods for aerial aircraft resupply
ES2929595T3 (en) 2020-10-29 2022-11-30 Airbus Defence & Space Sau Active air-to-air refueling system and method for generating aerodynamic radial loads at a hose end

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859002A (en) 1954-03-05 1958-11-04 Boeing Co Airfoil aircraft interconnecting boom
US4072283A (en) * 1976-12-17 1978-02-07 The Boeing Company Aerial refueling boom articulation
US4231536A (en) * 1977-10-11 1980-11-04 The Boeing Company Airfoil for controlling refueling boom
US4586683A (en) 1979-03-12 1986-05-06 Mcdonnell Douglas Corporation Rolling aerial refueling boom
US5785276A (en) 1995-12-22 1998-07-28 The Boeing Company Actuated roll axis aerial refueling boom
US6994294B2 (en) * 2003-08-29 2006-02-07 Smiths Aerospace, Inc. Stabilization of a drogue body

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859002A (en) 1954-03-05 1958-11-04 Boeing Co Airfoil aircraft interconnecting boom
US4072283A (en) * 1976-12-17 1978-02-07 The Boeing Company Aerial refueling boom articulation
US4231536A (en) * 1977-10-11 1980-11-04 The Boeing Company Airfoil for controlling refueling boom
US4586683A (en) 1979-03-12 1986-05-06 Mcdonnell Douglas Corporation Rolling aerial refueling boom
US5785276A (en) 1995-12-22 1998-07-28 The Boeing Company Actuated roll axis aerial refueling boom
US6994294B2 (en) * 2003-08-29 2006-02-07 Smiths Aerospace, Inc. Stabilization of a drogue body

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8439311B2 (en) 2010-08-23 2013-05-14 The Boeing Company Aerial refueling boom and boom pivot
US11167860B2 (en) 2012-01-04 2021-11-09 Israel Aerospace Industries Ltd. Devices, systems and methods for refueling air vehicles
US10543929B2 (en) 2012-01-04 2020-01-28 Israel Aerospace Industries Ltd. Systems and method for air vehicles
US10421556B2 (en) 2012-01-04 2019-09-24 Israel Aerospace Industries Ltd. Devices, systems and methods for refueling air vehicles
US11834192B2 (en) 2012-01-04 2023-12-05 Israel Aerospace Industries Ltd. Devices, systems and methods for refueling air vehicles
US11180262B2 (en) 2012-01-04 2021-11-23 Israel Aerospace Industries Ltd. Devices, systems and methods for refueling air vehicles
US9457912B2 (en) 2012-01-04 2016-10-04 Israel Aerospace Industries Ltd. Systems and methods for air vehicles
US9573696B2 (en) 2012-01-04 2017-02-21 Israel Aerospace Industries Ltd. Systems and methods for air vehicles
US10479523B2 (en) 2012-01-04 2019-11-19 Israel Aerospace Industries Ltd. Systems and methods for air vehicles
US9150311B2 (en) 2012-01-04 2015-10-06 Israel Aerospace Industries Ltd. Systems and methods for air vehicles
US10427801B2 (en) 2012-01-04 2019-10-01 Israel Aerospace Industries Ltd. Devices, systems and methods for refueling air vehicles
US9132921B2 (en) * 2012-08-09 2015-09-15 The Boeing Company Refueling boom control system
US20140042274A1 (en) * 2012-08-09 2014-02-13 The Boeing Company Refueling Boom Control System
US9352846B2 (en) 2012-08-09 2016-05-31 The Boeing Company Refueling boom control system
US20160075441A1 (en) * 2014-09-12 2016-03-17 Ziad Ahmed Mohamed Ali Hussein Elsawah Aerial refueling navigable device, system and method
US10436583B1 (en) 2015-03-06 2019-10-08 The Boeing Company Boom elevation estimation using hoist cable system
US10132628B2 (en) 2015-03-06 2018-11-20 The Boeing Company Aerial refueling boom elevation estimation system
US10011181B2 (en) 2016-09-27 2018-07-03 Ford Global Technologies, Llc Vehicle-to-vehicle charging system
US11919655B2 (en) 2017-06-18 2024-03-05 Israel Aerospace Industries Ltd. System and method for refueling air vehicles
US11465768B2 (en) 2017-07-10 2022-10-11 Israel Aerospace Industries Ltd. Refueling device

Also Published As

Publication number Publication date
EP1784332A1 (en) 2007-05-16
ATE423062T1 (en) 2009-03-15
EP1784332B1 (en) 2009-02-18
WO2006085986A1 (en) 2006-08-17
US20070084968A1 (en) 2007-04-19
ES2321431T3 (en) 2009-06-05
DE602005012838D1 (en) 2009-04-02

Similar Documents

Publication Publication Date Title
EP1784332B1 (en) In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom
EP3204245B1 (en) A directional control system and method for a hybrid air and ground transportation vehicle
EP1736407B1 (en) Controllable refueling drogues and associated systems and methods
US6554229B1 (en) Aileron for fixed wing aircraft
EP3034393B1 (en) Trailing edge device with bell crank mechanism
US6824105B2 (en) Drogue for in-flight refueling
US7188807B2 (en) Refueling booms with multiple couplings and associated methods and systems
EP3204246B1 (en) Wing central panel of hybrid transportation vehicle for the ground and the air
US9108723B2 (en) Flap panel shuttle system and method therefor
US9004411B2 (en) Mechanical control mixer and method therefor
US8079545B2 (en) System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations
US9102395B2 (en) Multifunctional propulsive system for an airplane
US8317136B2 (en) Stabilized controllable drogue for aerial flight refueling
WO2014209714A1 (en) Mechanism for trailing edge control surface
EP2078672B1 (en) System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations
US20230182921A1 (en) Device for refueling air vehicles
WO2023112023A1 (en) Boom member for refueling air vehicles

Legal Events

Date Code Title Description
AS Assignment

Owner name: BOEING COMPANY, THE, ILLINOIS

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:THAL, GERMAN VON;SLUSHER, HARRY W.;REEL/FRAME:015615/0780

Effective date: 20040722

STCF Information on status: patent grant

Free format text: PATENTED CASE

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

FPAY Fee payment

Year of fee payment: 4

FPAY Fee payment

Year of fee payment: 8

FEPP Fee payment procedure

Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

LAPS Lapse for failure to pay maintenance fees

Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362

FP Lapsed due to failure to pay maintenance fee

Effective date: 20190724